超燃燃烧室气流参数诊断

基于可调谐二极管激光器吸收光谱技术, 利用7185.597cm^{-1}, 7444.35cm^{-1} + 7444.37cm^{-1}(重合吸收线)两条H_2O吸收线, 采用分时扫描-直接探测策略组建多光路吸收测量系统, 在4kHz的测量频率下, 定量测量了燃烧室气流的静温、水蒸气浓度和流向速度. 利用位移机构, 在以C_2H_4为燃料的超燃直连式试验台中, 在单次试验中同时诊断燃烧室内某截面和燃烧室出口的多气流参数的截面分布. 利用燃烧室出口截面的水蒸气浓度分布, 并结合壁面静压计算燃烧效率; 利用燃烧室出口截面的静温和速度分布, 获得出口气流马赫数分布; 利用凹腔后部某截面的温度和水蒸气浓度分布, 判读了凹腔附近流场特征.      

叠片式气体箔片推力轴承热特性分析

叠片式气体箔片推力轴承具有制造工艺简单、散热能力强等优点，针对该新型轴承提出了相应的热特性分析模型，通过数值仿真分析得到轴承气膜及各元件的温度，并对关键影响参数进行了重点分析. 研究结果表明:由于气膜在半径较大位置处的线速度大，其剪切产热效果明显，温度越高，气膜的高温区分布在靠近周向末端和顶箔侧；气膜、顶箔和推力盘温度均会随推力盘转速和轴承载荷的增大而升高；向箔片结构中通入冷却气流可以获得良好的降温效果，轴承温度随着箔片内通入冷却气流量的增大，先迅速下降后趋于平缓.      

基于TDLAS的层析成像技术TDLAT

可调谐二极管吸收光谱技术（tunable diode laser absorption spectroscopy,TDLAS）已成为超声速燃烧的重要测量手段之一. 为提高其空间分辨能力,需发展基于TDLAS,结合层析成像术的二维断层成像术（tunablediode laser absorption tomography, TDLAT）. 设计了一套基于6 平行光束-旋转测量的新型TDLAT 系统,吸收波长为7 185.6 cm-1 和7 444.3 cm-1 双线,采用分时-直接吸收探测策略. 重建中,使用代数重建算法,先分别反演计算两吸收线的吸收率和吸收比分布,再获得温度和浓度分布. 利用该系统,在CH₄/Air 预混平面燃烧炉上开展初步验证试验. 结果表明,TDLAT 系统可以反演出温度和浓度分布特征,反演的温度分布结果与热电偶测量值吻合较好. 进一步改进该系统,可用于超燃直连台中,测量燃烧室出口气流的温度和组分浓度分布.      

基于TDLAS的层析成像技术TDLAT简

可调谐二极管吸收光谱技术（tunable diode laser absorption spectroscopy，TDLAS）已成为超声速燃烧的重要测量手段之一. 为提高其空间分辨能力，需发展基于TDLAS，结合层析成像术的二维断层成像术（tunablediode laser absorption tomography, TDLAT）. 设计了一套基于6 平行光束-旋转测量的新型TDLAT 系统，吸收波长为7 185.6 cm^-1 和7 444.3 cm^-1 双线，采用分时-直接吸收探测策略. 重建中，使用代数重建算法，先分别反演计算两吸收线的吸收率和吸收比分布，再获得温度和浓度分布. 利用该系统，在CH₄/Air 预混平面燃烧炉上开展初步验证试验. 结果表明，TDLAT 系统可以反演出温度和浓度分布特征，反演的温度分布结果与热电偶测量值吻合较好. 进一步改进该系统，可用于超燃直连台中，测量燃烧室出口气流的温度和组分浓度分布.     

燃烧轻气炮多级渐扩型燃烧室流场特性数值研究

为了分析多级渐扩型燃烧室结构对燃烧轻气炮氢氧燃烧特性的影响, 通过计算流体力学方法, 分别对采用传统圆柱型燃烧室和多级渐扩型燃烧室的燃烧轻气炮氢氧燃烧发射过程进行数值模拟。对比结果表明, 多级渐扩型燃烧室结构能够明显地减小燃烧室压力波动幅度, 提高氢氧燃烧稳定性; 多级渐扩型燃烧室内形成回流区, 可以减小气流轴向运动速度; 火焰扩展形态与渐扩型结构相吻合, 燃烧反应区表面变化平稳; 多级渐扩型燃烧室结构对氢氧火焰传播过程和压力波动现象有着重要影响。     

当量比对预混燃烧影响的大涡模拟研究

本文对在突扩燃烧室内甲烷和空气的预混燃烧进行了大涡模拟(LES)研究,考虑预混燃料的当量比对燃烧室提供的动力及产生的污染物的影响．利用LES计算了不同当量比条件下燃烧室内湍流预混燃烧反应流场的温度、浓度、涡量和压力分布,最后对当量比0.5时B点和C点的温度和速度进行EMD分解,得到了温度场和速度场的各阶模态的平均周期．结果表明：随着当量比从0.5增加至0.7,燃烧反应趋于剧烈,燃烧室的最高温度提高了350K,平均压力从32.876 Pa增大到34.833Pa,燃烧产生的瞬态径向最高浓度从0.5%增加到0.95%．     

地震纵横波时差耦合作用的斜坡崩滑效应研究

在燃烧室入口来流为Ma=2.64、T0=1483K、P0＝1.65MPa、T=724K、P=76.3kPa条件下,采用高速摄影和连续激光高速纹影对等截面型开窗燃烧室内氢气射流自燃过程、火花塞点燃氢气过程和引导氢气火焰点燃煤油过程进行了观测,获得了燃烧室内着火过程中火焰和流场波系结构的动态演化过程;观察到了初始火焰区首先起始于燃烧室下游,并逆流传播实现发动机着火的过程;分析表明燃料能否着火、以及着火位置与燃料着火时间、燃烧室流速和火焰稳定器安装情况相关,多火焰稳定区延长了燃料驻留时间,使燃料更容易着火。 关键词 超燃冲压发动机,点火过程,火焰传播,火焰稳定器     

高超声速边界层液膜演化过程和冷却机理研究

高超声速液膜冷却技术是通过一系列狭缝或孔洞压出冷却工质,在飞行器表面边界层形成一层低温冷却膜,阻止高超声速气流对飞行器的气动加热.其作为一种主动冷却方式在高超声速飞行器表面热防护有着巨大的应用潜力.文章采用数值方法,结合VOF模型,研究25 km飞行高度和Ma=5气流条件下的液膜铺展情况,并通过不同冷却工质的入射速度、角度、表面张力和黏性系数条件,讨论了液膜在平板上的演化过程和冷却机理.结果表明,在气流作用下,液膜向壁面下游发展,液膜的存在导致边界层分离,连续液膜会在一定位置断裂为液块,然后进一步破碎为液滴.入射条件和液体性质的改变,会影响液膜沿流向的发展,具体表现在连续液膜断裂点的位置和连续液膜的厚度.在所设定的计算域内,壁面热流降低了80%～95%,液膜对壁面的冷却效率随着液膜形态的变化而变化.     

模型超燃冲压发动机内着火过程分析

在燃烧室入口来流为Ma=2.64、T0=1483K、P0＝1.65MPa、T=724K、P=76.3kPa条件下,采用高速摄影和连续激光高速纹影对等截面型开窗燃烧室内氢气射流自燃过程、火花塞点燃氢气过程和引导氢气火焰点燃煤油过程进行了观测,获得了燃烧室内着火过程中火焰和流场波系结构的动态演化过程;观察到了初始火焰区首先起始于燃烧室下游,并逆流传播实现发动机着火的过程;分析表明燃料能否着火、以及着火位置与燃料着火时间、燃烧室流速和火焰稳定器安装情况相关,多火焰稳定区延长了燃料驻留时间,使燃料更容易着火。关键词 超燃冲压发动机,点火过程,火焰传播,火焰稳定器      

温度作用下煤体裂隙演化规律数值模拟及声发射特性研究

温度的作用会在煤体上产生热应力, 进而引发煤体的裂隙发育乃至引发破裂, 有利于瓦斯的抽采.利用RFPA 有限元软件模拟加温热处理时煤体的破裂过程, 观察不同温度下煤体破裂的裂纹裂隙发展规律.采用声发射的试验方法对不同围压下温度改变时煤体内部裂隙发展进行细微观察并与RFPA 数值模拟结果进行对比. 研究结果表明: 温度改变产生的热应力能够使煤体温度升高, 进而破坏原有割理系统产生新的裂隙裂纹; 当温度达到一定值时, 煤体内部孔隙裂隙发育扩展较为明显, 形成主裂纹, 有效渗透通道增加, 降低煤体对气体分子的吸附能力, 提高游离气体含量, 渗透率明显提高. 该研究可为预防瓦斯相关灾害和瓦斯的抽采提供理论参考.     

Reconstructed 3D flame structures in noise-controlled swirl-stabilized combustor

Flame structures of turbulent premixed flames in a noise-controlled, swirl-stabilized combustor are investigated to clarify the mechanism of combustion noise reduction by the secondary fuel injection. Planar laser-induced fluorescence (PLIF) is conducted for several cases with different secondary fuel injection, and 3D flame structure is reconstructed from PLIF results on multiple planes. The secondary fuel injection suppresses the fluctuation of high-temperature gas in the recirculation zone and reduces Reynolds stress and entropy terms in the acoustic sound source. In the flame zone, effects of the injection frequency are discussed by introducing mean progress variable. The flame brush is very wide for the no control case, whereas it becomes thin and is confined to a narrow space for the secondary fuel injection cases. The investigated combustor gives minimum sound level at a relevant fuel injection frequency, which is very low compared with the natural acoustic mode of the combustor. The flame brush becomes very thin, and self-induced oscillations of the flame brush disappear at this relevant frequency. The oscillation of the flame brush represents large-scale fluctuation of the mean heat release rate. The relations between characteristics of flame brush and combustion noise are discussed by introducing instantaneous and dynamical effects of flame front on the entropy term of the sound source. The secondary fuel injection works for the control of the entropy term in the sound source because the thin flame brush represents suppression of the instantaneous and dynamical effects.     

A new phenomenon of acoustic streaming

This paper describes a new phenomenon of acoustic streaming which takes place when a Helmholtz resonator is excited by an inside sound source with resonant frequency, and takes the form of a strong turbulent jet. The flow visualizations, hot wire and LDV measurements are combined to investigate the process of acoustic streaming. It is found that this kind of acoustic streaming results from the contribution of Reynolds stress.     

声学整流效应的新现象

本文描述了一种新的声学整流效应现象,当Helmholtz共振腔内部声源以共振频率激振时,整流以一股湍流喷流形式发生。流动显示、热线和激光测量结合起来对此声学整流过程进行了研究,结果表明整流是由Reynolds应力作用产生的。     

Cool sound: the future of refrigeration? Thermodynamic and heat transfer issues in thermoacoustic refrigeration

During the past two decades the thermoacoustic refrigeration and prime mover cycles gained importance in a variety of refrigeration applications. Acoustic work, sound, can be used to generate temperature differences that allow the transport of heat from a low temperature reservoir to an ambient at higher temperature, thus forming a thermoacoustic refrigeration system. The thermoacoustic energy pumping cycle can also be reversed: temperature difference imposed along the stack plates can lead to sound generation. In this situation the thermoacoustic system operates as a prime mover. Sound generated by means of this thermoacoustic energy conversion process can be utilized to drive different types of refrigeration devices that require oscillatory flow for their operation, such as thermoacoustic refrigerators, pulse tubes and Stirling engines. In order for a thermoacoustic refrigeration or prime mover system as well as a thermoacoustic prime mover driving a non-thermoacoustic refrigeration system to be competitive on the current market, it has to be optimized in order to improve its overall performance. Optimization can involve improving the performance of the entire system as well as its components. The paper addresses some of the thermodynamic and heat transfer issues relevant in improving the performance of the thermoacoustic system, such as optimization for maximum COP, maximum cooling load and the role of the heat exchangers. Results obtained using the two optimization criteria are contrasted in the paper to illustrate the complexity of the optimization process.     

Measurement of acoustic velocity in the stack of a thermoacoustic refrigerator using particle image velocimetry

Thermoacoustic refrigeration systems generate cooling power from a high-amplitude acoustic standing wave. There has recently been a growing interest in this technology because of its simple and robust architecture and its use of environmentally safe gases. With the prospect of commercialization, it is necessary to enhance the efficiency of thermoacoustic cooling systems and more particularly of some of their components such as the heat exchangers. The characterization of the flow field at the end of the stack plates is a crucial step for the understanding and optimization of heat transfer between the stack and the heat exchangers. In this study, a specific particle image velocimetry measurement is performed inside a thermoacoustic refrigerator. Acoustic velocity is measured using synchronization and phase-averaging. The measurement method is validated inside a void resonator by successfully comparing experimental data with an acoustic plane wave model. Velocity is measured inside the oscillating boundary layers, between the plates of the stack, and compared to a linear model. The flow behind the stack is characterized, and it shows the generation of symmetric pairs of counter-rotating vortices at the end of the stack plates at low acoustic pressure level. As the acoustic pressure level increases, detachment of the vortices and symmetry breaking are observed.     

Dispersion of Entropy Perturbations Transporting through an Industrial Gas Turbine Combustor

In the context of combustion noise and combustion instabilities, the transport of entropy perturbations through highly simplified turbulent flows has received much recent attention. This work performs the first systematic study into the transport of entropy perturbations through a realistic gas turbine combustor flow-field, exhibiting large-scale hydrodynamic flow features in the form of swirl, separation, recirculation zones and vortex cores, these being ubiquitous in real combustor flows. The reacting flow-field is simulated using low Mach number large eddy simulations, with simulations validated by comparison to available experimental data. A generic artificial entropy source, impulsive in time and spatially localized at the flame-front location, is injected. The conservation equation describing entropy transport is simulated, superimposed on the underlying flow-field simulation. It is found that the transport of entropy perturbations is dominated by advection, with both thermal diffusion and viscous production being negligible. It is furthermore found that both the mean flow-field and the large-scale unsteady flow features contribute significantly to advective dispersion — neither can be neglected. The time-variation of entropy perturbation amplitude at combustor exit is well-modelled by a Gaussian profile, whose dispersion exceeds that corresponding to a fully-developed pipe mean flow profile roughly by a factor of three. Finally, despite the attenuation in entropy perturbation amplitude caused by advective dispersion, sufficient entropy perturbation strength is likely to remain at combustor exit for entropy noise to make a meaningful contribution at low frequencies.     

Modeling and simulation of an acoustic well stimulation method

This paper presents a mathematical model and a numerical procedure to simulate an acoustic well stimulation (AWS) method for enhancing the permeability of the rock formation surrounding oil and gas wells. The AWS method considered herein aims to exploit the well-known permeability-enhancing effect of mechanical vibrations in acoustically porous materials, by transmitting time-harmonic sound waves from a sound source device—placed inside the well—to the well perforations made into the formation. The efficiency of the AWS is assessed by quantifying the amount of acoustic energy transmitted from the source device to the rock formation in terms of the emission frequency and the well configuration. A simple methodology to find optimal emission frequencies for a given well configuration is presented. The proposed model is based on the Helmholtz equation, a sound-hard boundary condition at the casing, and an impedance boundary condition that effectively accounts for the porous solid–fluid interaction at the interface between the rock formation and the well perforations. Exact non-reflecting boundary conditions derived from Dirichlet-to-Neumann maps are utilized to truncate the circular cylindrical waveguides considered in the model. The resulting boundary value problem is then numerically solved by means of the finite element method. A variety of numerical examples are presented in order to demonstrate the effectiveness of the proposed procedure for finding optimal emission frequencies.     

Simulation of thermoacoustic waves by a pressure-based algorithm for compressible flows

A modified SIMPLEC method which can solve compressible flows at low Mach number is introduced and used to study thermoacoustic waves induced by a rapid change of temperature at a solid wall and alternatingdirection flows generated by thermoacoustic effects in a tapered resonator.The results indicate that the algorithm adopted in this paper can be used for calculating compressible flows and thermoacoustic waves.It is found that the pressure and velocity in the resonator behave as standing waves,and the tapered resonator can suppress highfrequency harmonic waves as observed in a cylindrical resonator.     

Direct numerical modeling of time-reversal acoustic subwavelength focusing

Focusing waves back to their original source position is possible both experimentally and numerically thanks to time reversal mirrors (TRM). For a TRM placed in the far field of the source, the focusing spot of the reversed wavefield is subject to the diffraction limit and cannot be smaller than half the minimum wavelength, even for a very small source. Yet, numerous time reversal experiments in resonating media have shown subwavelength focusing. In this work, we show that it is possible to model these subwavelength focusing observations with simple physics, only the 2-D standard acoustic wave equation, and with specific fine scale heterogeneity. Our work is based on the spectral element method to solve the wave equation and to model time reversal experiments. Such a method makes it possible to propagate very long time series in complex and strongly discontinuous media with high accuracy. The acoustic wave equations are solved at the fine scale in media with one or more split rings of size much smaller than the wavelength. Such split rings produce a Helmholtz resonance effect as well as propagation band-gaps. We show that, in such media, even with a single split ring resonator, subwavelength focusing down to 1/13th of the minimum wavelength can be observed.     

Réduction semi-active du battement de volume généré par une cavité profonde soumise à un écoulement aérodynamiqueSemi-active reduction of the sound generated by a deep cavity under an airflow

We present experimental results obtained with a deep cavity, such as a Helmholtz resonator, excited by an airflow. The resonance under the action of the vortices generated in the shear layer is well described and quantified. The mounting of actuators, based on a few piezo-electric elements, allows us to generate a series of two-dimensional vortices forced at a frequency which is different than the natural resonance frequency. The sound level in the cavity is strongly decreased and only the broadband noise of the turbulence remains. To cite this article: X. Amandolese et al., C. R. Mecanique 330 (2002) 101–106.